大气制动期间探测器的气动特性和轨道计算  

Spacecraft Aerodynamics and Trajectory Simulation During Aerobraking

作　　者：张文普[1] 韩波[1] 张成义[1] 

机构地区：[1]浙江大学航空航天学院流体工程研究所,杭州310027

出　　处：《应用数学和力学》2010年第9期1016-1026,共11页Applied Mathematics and Mechanics

基　　金：航天科技CAST基金资助项目(CAST2006023)

摘　　要：以NASA火星全球勘测(MGS)号探测器作为大气制动计算模型,应用DSMC方法模拟了探测器在大气制动期间的稀薄气体动力学特性,分析了不同来流密度情况下探测器的流场特性、气动特性的变化情况以及气体动力学系数的变化关系.并提出了气动力-气动热-轨道一体化计算模型,利用DSMC模拟技术以及经典动力学理论对大气制动轨道变化进行了计算和分析.研究结果表明:行星大气密度、探测器俯仰角、偏航角的变化对探测器的气动特性有重要影响,计算结果与文献中的结果表现出很好的一致性;气动力-气动热-轨道一体化计算可以模拟大气制动过程,模拟所得到的大气制动轨迹反映出较好的制动效果.The direct simulation Monte Carlo method（DSMC） was used to simulate rarefied aerodynamic characteristics during the aerobraking process of NASA Mars Global Surveyor（MGS） spacecraft.The research focused on the flowfield and aerodynamic characteristics distribution under various freestream densities,and the variation regularity of aerodynamic coefficients was analyzed.Also,an aerodynamics-aeroheating-trajectory integrative simulation model was developed to preliminarily calculate the aerobraking orbit transfer by combining DSMC technique and classical kinematics theory.Results show that the effect of planetary atmospheric density,spacecraft yaw and pitch attitudes on the spacecraft aerodynamics is significant.The numerical results are in good agreement with the existing results in the literature.The aerodynamics-aeroheating-trajectory integrative simulation model is proved to be able to simulate the orbit transfer in the complete aerobraking mission,and current results of spacecraft trajectory show that the aerobraking maneuvers give good performance of attitude control.

关 键 词：大气制动 稀薄气体动力学 DSMC方法 火星探测器 气动特性 轨道计算 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程] V412.41